GOE 393 AIRFOIL (goe393-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 393 AIRFOIL (goe393-il) Reynolds number: 100,000 Max Cl/Cd: 55.91 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe393-il-100000.txt Download as CSV file: xf-goe393-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 393 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4583 0.10800 0.10323 0.0139 1.0000 0.0705
-8.000 -0.4577 0.10698 0.10228 0.0089 1.0000 0.0725
-7.750 -0.4529 0.10664 0.10199 -0.0023 1.0000 0.0732
-7.500 -0.4439 0.10067 0.09606 -0.0018 1.0000 0.0740
-7.250 -0.4333 0.09505 0.09045 0.0034 1.0000 0.0755
-7.000 -0.4222 0.09134 0.08676 0.0031 1.0000 0.0775
-6.750 -0.4103 0.08796 0.08340 0.0008 1.0000 0.0799
-6.500 -0.3961 0.08471 0.08015 -0.0035 1.0000 0.0832
-6.250 -0.3609 0.08390 0.07915 -0.0227 1.0000 0.0867
-6.000 -0.3588 0.07744 0.07284 -0.0163 1.0000 0.0880
-5.750 -0.3471 0.07361 0.06906 -0.0149 1.0000 0.0902
-5.500 -0.3299 0.07024 0.06568 -0.0167 1.0000 0.0932
-5.250 -0.3034 0.06720 0.06255 -0.0228 1.0000 0.0985
-5.000 -0.2714 0.06366 0.05883 -0.0308 1.0000 0.1013
-4.750 -0.2611 0.05971 0.05501 -0.0286 1.0000 0.1036
-4.500 -0.2416 0.05678 0.05208 -0.0295 1.0000 0.1086
-4.250 -0.2031 0.05411 0.04911 -0.0371 1.0000 0.1154
-4.000 -0.1895 0.05048 0.04560 -0.0361 1.0000 0.1174
-3.750 -0.1709 0.04787 0.04304 -0.0364 1.0000 0.1215
-3.500 -0.1442 0.04631 0.04124 -0.0399 1.0000 0.1296
-3.250 -0.1194 0.04289 0.03798 -0.0423 0.9879 0.1342
-2.750 -0.0121 0.03634 0.03096 -0.0565 0.9437 0.1612
-2.500 0.0281 0.03391 0.02832 -0.0598 0.9145 0.1759
-2.250 0.0590 0.03193 0.02617 -0.0608 0.8858 0.1920
-2.000 0.0847 0.03043 0.02445 -0.0607 0.8603 0.2192
-1.750 0.1062 0.02887 0.02279 -0.0596 0.8382 0.2501
-1.500 0.1534 0.00975 0.00254 -0.0581 0.7919 0.1295
-1.250 0.1908 0.02318 0.01500 -0.0607 0.8046 0.1138
-1.000 0.2182 0.02183 0.01328 -0.0600 0.7877 0.1138
-0.750 0.2436 0.02084 0.01222 -0.0595 0.7718 0.1207
-0.500 0.2716 0.02011 0.01105 -0.0586 0.7571 0.1281
-0.250 0.2980 0.01915 0.00998 -0.0580 0.7432 0.1374
0.000 0.3250 0.01850 0.00910 -0.0572 0.7297 0.1563
0.250 0.3512 0.01798 0.00858 -0.0568 0.7160 0.1781
0.500 0.3777 0.01784 0.00837 -0.0563 0.7026 0.2015
0.750 0.4044 0.01760 0.00812 -0.0558 0.6898 0.2164
1.000 0.4307 0.01733 0.00790 -0.0552 0.6774 0.2251
1.250 0.4571 0.01721 0.00774 -0.0544 0.6655 0.2333
1.500 0.4837 0.01717 0.00765 -0.0538 0.6543 0.2463
1.750 0.5105 0.01713 0.00768 -0.0534 0.6419 0.2625
2.000 0.5374 0.01711 0.00777 -0.0531 0.6303 0.2878
2.250 0.5694 0.01565 0.00776 -0.0534 0.6192 1.0000
2.500 0.5963 0.01598 0.00781 -0.0527 0.6091 1.0000
2.750 0.6232 0.01636 0.00811 -0.0524 0.5977 1.0000
3.000 0.6499 0.01677 0.00845 -0.0521 0.5880 1.0000
3.250 0.6764 0.01713 0.00870 -0.0515 0.5792 1.0000
3.500 0.7030 0.01758 0.00918 -0.0513 0.5686 1.0000
3.750 0.7295 0.01800 0.00957 -0.0509 0.5608 1.0000
4.000 0.7561 0.01849 0.01011 -0.0507 0.5518 1.0000
4.250 0.7824 0.01894 0.01058 -0.0504 0.5427 1.0000
4.500 0.8081 0.01906 0.01062 -0.0494 0.5315 1.0000
4.750 0.8336 0.01904 0.01055 -0.0484 0.5175 1.0000
5.000 0.8590 0.01904 0.01055 -0.0475 0.5029 1.0000
5.250 0.8847 0.01922 0.01081 -0.0468 0.4900 1.0000
5.500 0.9105 0.01954 0.01125 -0.0464 0.4791 1.0000
5.750 0.9364 0.01976 0.01154 -0.0457 0.4685 1.0000
6.000 0.9623 0.01984 0.01162 -0.0449 0.4570 1.0000
6.250 0.9878 0.01991 0.01178 -0.0442 0.4433 1.0000
6.500 1.0132 0.01998 0.01197 -0.0434 0.4286 1.0000
6.750 1.0382 0.02004 0.01216 -0.0425 0.4116 1.0000
7.000 1.0625 0.01996 0.01222 -0.0415 0.3886 1.0000
7.250 1.0855 0.01971 0.01195 -0.0402 0.3554 1.0000
7.500 1.1065 0.01979 0.01205 -0.0390 0.3023 1.0000
7.750 1.1259 0.02054 0.01254 -0.0379 0.2366 1.0000
8.000 1.1432 0.02197 0.01360 -0.0370 0.1875 1.0000
8.250 1.1575 0.02393 0.01522 -0.0358 0.1548 1.0000
8.500 1.1708 0.02614 0.01730 -0.0344 0.1222 1.0000
8.750 1.1831 0.02850 0.01945 -0.0329 0.0977 1.0000
9.000 1.1984 0.03066 0.02159 -0.0314 0.0830 1.0000
9.250 1.2155 0.03291 0.02369 -0.0302 0.0737 1.0000
9.500 1.2332 0.03466 0.02571 -0.0289 0.0665 1.0000
9.750 1.2521 0.03714 0.02804 -0.0280 0.0616 1.0000
10.000 1.2704 0.03972 0.03098 -0.0267 0.0588 1.0000
10.250 1.2864 0.04222 0.03378 -0.0255 0.0558 1.0000
10.500 1.3006 0.04439 0.03611 -0.0244 0.0527 1.0000
10.750 1.3150 0.04835 0.04011 -0.0238 0.0505 1.0000
11.000 1.3207 0.05187 0.04408 -0.0223 0.0499 1.0000
11.250 1.3213 0.05566 0.04832 -0.0207 0.0495 1.0000
11.500 1.3167 0.05969 0.05275 -0.0192 0.0494 1.0000
11.750 1.3067 0.06377 0.05717 -0.0177 0.0494 1.0000
12.000 1.2916 0.06782 0.06150 -0.0165 0.0495 1.0000
12.250 1.2742 0.07232 0.06624 -0.0164 0.0497 1.0000
12.500 1.2556 0.07741 0.07154 -0.0176 0.0499 1.0000
12.750 1.2365 0.08313 0.07745 -0.0197 0.0501 1.0000
13.000 1.2175 0.08948 0.08395 -0.0223 0.0504 1.0000
13.250 1.1891 0.09611 0.09088 -0.0277 0.0511 1.0000
13.750 0.9203 0.11664 0.11195 -0.0305 0.0605 1.0000
14.000 0.8204 0.14037 0.13566 -0.0443 0.0721 1.0000
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Polar data table (+)
Polar graphs
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